SLEWING FLEXIBLE SPACECRAFT WITH DEFLECTION-LIMITING INPUT SHAPING

A control scheme is described for slewing flexible spacecraft with bot h suppression of deflection during the slew and elimination of residua l oscillations. The method minimizes the maneuver time subject to cons traints on residual vibration magnitude, sensitivity to modeling error s, rest-to-rest slew distance, and the transient deflection amplitude. Furthermore, a solution is sought that provides inherent fuel efficie ncy. The feasibility of the approach is demonstrated with linear and n onlinear computer simulations.